Turbine shroud with containment features

Abstract

An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.

What is claimed is: 
     
       1. A turbine shroud adapted for use in a gas turbine engine, the turbine shroud comprising
 a carrier comprising metallic materials arranged to extend circumferentially at least partway about a center axis, 
 a first turbine shroud segment including a first blade track segment comprising ceramic matrix composite materials and a first intermediate carrier configured to couple the first blade track segment to the carrier, the first blade track segment formed to include a first runner shaped to extend circumferentially partway around the center axis, a first fore mount post that extends radially outward from the first runner, and a first aft mount post that extends radially outward from the first runner, the first aft mount post spaced apart axially from the first fore mount post to define a first channel therebetween, and the first intermediate carrier including a first intermediate carrier body arranged in the first channel axially between the first fore mount post and the first aft mount post and at least two first intermediate carrier pins that each extend axially into the first fore mount post, the first intermediate carrier body, and the first aft mount post to couple the first intermediate carrier body to the first blade track segment, and 
 a second turbine shroud segment arranged circumferentially adjacent to the first turbine shroud segment, the second turbine shroud segment including a second blade track segment comprising ceramic matrix composite materials and a second intermediate carrier configured to couple the second blade track segment to the carrier, the second blade track segment formed to include a second runner shaped to extend circumferentially partway around the center axis, a second fore mount post that extends radially outward from the second runner, and a second aft mount post that extends radially outward from the second runner, the second aft mount post spaced apart axially from the second fore mount post to define a second channel therebetween, and the second intermediate carrier including a second intermediate carrier body arranged in the second channel axially between the second fore mount post and the second aft mount post and at least two second intermediate carrier pins that each extend axially into the second fore mount post, the second intermediate carrier body, and the second aft mount post to couple the second intermediate carrier body to the second blade track segment, 
 wherein the second intermediate carrier body is shaped to define a flange that extends circumferentially from a circumferential end of the second intermediate carrier body into a groove formed in an adjacent circumferential end of the first intermediate carrier body so that one pin of the at least two first intermediate carrier pins extends axially through the first intermediate carrier body and the flange of the second intermediate carrier body to form a joint between the first intermediate carrier and the second intermediate carrier that couples the first intermediate carrier to the second intermediate carrier to share loading therebetween and close a gap between the first turbine shroud segment and the second turbine shroud segment. 
 
     
     
       2. The turbine shroud of  claim 1 , wherein the first intermediate carrier further includes a plurality of first intermediate carrier retainers that each extend radially and couple the first intermediate carrier body with the carrier, and the second intermediate carrier further includes a plurality of second intermediate carrier retainers that each extend radially and couple the second intermediate carrier body with the carrier. 
     
     
       3. The turbine shroud of  claim 2 , wherein the plurality of first intermediate carrier retainers includes two first intermediate carrier retainers and the plurality of second intermediate carrier retainers includes two second intermediate carrier retainers. 
     
     
       4. The turbine shroud of  claim 2 , wherein the second intermediate carrier body is shaped to include a forward side surface and an aft side surface spaced apart axially from the forward side surface, the circumferential end extends between and interconnects the forward side surface and the aft side surface, and edges of the flange are spaced apart axially from the forward side surface and the aft side surface of the second intermediate carrier body. 
     
     
       5. The turbine shroud of  claim 2 , wherein the first intermediate carrier body is shaped to include a flange that extends circumferentially from the adjacent circumferential end of the first intermediate carrier body to form the groove, the flange of the first intermediate carrier body extends into a groove formed by the flange of the second intermediate carrier body to engage the flange of the second intermediate carrier body, and the one pin of the at least two first intermediate carrier pins extends axially through the flange of the first intermediate carrier body and the flange of the second intermediate carrier body to form the joint. 
     
     
       6. The turbine shroud of  claim 5 , wherein the flange of the second intermediate carrier body axially overlaps the flange of the first intermediate carrier body. 
     
     
       7. The turbine shroud of  claim 1 , wherein edges of the flange of the second intermediate carrier are spaced apart axially from edges of the circumferential end of the second intermediate carrier body. 
     
     
       8. The turbine shroud of  claim 1 , wherein the first intermediate carrier body is shaped to include a flange that extends circumferentially from the adjacent circumferential end of the first intermediate carrier body to form the groove, the flange of the first intermediate carrier body extends into a groove formed by the flange of the second intermediate carrier body to engage the flange of the second intermediate carrier body. 
     
     
       9. The turbine shroud of  claim 8 , wherein the flange of the second intermediate carrier body axially overlaps the flange of the first intermediate carrier body so that the one pin of the at least two first intermediate carrier pins extends axially through the flange of the first intermediate carrier body and the flange of the second intermediate carrier body to form the joint. 
     
     
       10. A turbine shroud adapted for use in a gas turbine engine, the turbine shroud comprising
 a first turbine shroud segment including a first carrier, a first blade track segment, and a first intermediate carrier configured to couple the first blade track segment to the first carrier, the first blade track segment formed to include a first runner shaped to extend circumferentially partway around a center axis of the gas turbine engine and a first attachment portion that extends radially outward from the first runner, and the first intermediate carrier includes a first intermediate carrier body arranged adjacent to the first attachment portion and a first intermediate carrier pin that extends axially through the first attachment portion and the first intermediate carrier body to couple the first intermediate carrier body to the first blade track segment, and 
 a second turbine shroud segment arranged circumferentially adjacent to the first turbine shroud segment, the second turbine shroud segment including a second carrier, a second blade track segment, and a second intermediate carrier configured to couple the second blade track segment to the second carrier, the second blade track segment formed to include a second runner shaped to extend circumferentially partway around the center axis and a second attachment portion that extends radially outward from the second runner, and the second intermediate carrier includes a second intermediate carrier body arranged adjacent to the second attachment portion and a second intermediate carrier pin that extends axially through the first attachment portion and the second intermediate carrier body to couple the second intermediate carrier body to the second blade track segment, 
 wherein the second intermediate carrier body is shaped to define a flange that extends circumferentially from a circumferential end of the second intermediate carrier body into a groove formed in an adjacent circumferential end of the first intermediate carrier body so that the first intermediate carrier pin extends axially through the first intermediate carrier body and the flange of the second intermediate carrier body to form a joint between the first intermediate carrier and the second intermediate carrier. 
 
     
     
       11. The turbine shroud of  claim 10 , wherein the first intermediate carrier further includes a plurality of first intermediate carrier retainers that each extend radially and couple the first intermediate carrier body with the carrier, and the second intermediate carrier further includes a plurality of second intermediate carrier retainers that each extend radially and couple the second intermediate carrier body with the carrier. 
     
     
       12. The turbine shroud of  claim 11 , wherein the second intermediate carrier body is shaped to include a forward side surface and an aft side surface spaced apart axially from the forward side surface, the circumferential end extends between and interconnects the forward side surface and the aft side surface, and edges of the flange are spaced apart axially from the forward side surface and the aft side surface of the second intermediate carrier body. 
     
     
       13. The turbine shroud of  claim 11 , wherein the first intermediate carrier body is shaped to include a flange that extends circumferentially from the adjacent circumferential end of the first intermediate carrier body to form the groove, the flange of the first intermediate carrier body extends into a groove formed by the flange of the second intermediate carrier body to engage the flange of the second intermediate carrier body. 
     
     
       14. The turbine shroud of  claim 13 , wherein the flange of the second intermediate carrier body axially overlaps the flange of the first intermediate carrier body such that the one pin of the at least two first intermediate carrier pins extends axially through the flange of the first intermediate carrier body and the flange of the second intermediate carrier body to form the joint. 
     
     
       15. The turbine shroud of  claim 10 , wherein edges of the flange of the second intermediate carrier are spaced apart axially from edges of the circumferential end of the second intermediate carrier body. 
     
     
       16. The turbine shroud of  claim 10 , wherein the first intermediate carrier body is shaped to include a flange that extends circumferentially from the adjacent circumferential end of the first intermediate carrier body to form the groove, the flange of the first intermediate carrier body extends into a groove formed by the flange of the second intermediate carrier body to engage the flange of the second intermediate carrier body, and the one pin of the at least two first intermediate carrier pins extends axially through the flange of the first intermediate carrier body and the flange of the second intermediate carrier body to form the joint. 
     
     
       17. A method comprising
 providing a plurality of blade track segments, a plurality of intermediate carrier bodies, and a plurality of intermediate carrier pins, each blade track segment including a runner shaped to extend partway around an axis, a fore mount post that extends radially outward from the first runner, and an aft mount post spaced apart axially from the fore mount post that extends radially outward from the runner, 
 arranging a first intermediate carrier body of the plurality of intermediate carrier bodies axially between the fore mount post and the aft mount post of a first blade track segment included in the plurality of blade track segments, 
 inserting the one pin of the plurality of intermediate carrier pins axially through the fore mount post, the first intermediate carrier body, and the aft mount post to couple the first blade track segment to the first intermediate carrier body, 
 arranging a second intermediate carrier body circumferentially adjacent to the first intermediate carrier body so that a flange formed by the second intermediate carrier body extends into a groove formed in the first intermediate carrier body, 
 inserting another pin of the plurality of intermediate carrier pins axially through the fore mount post, the first intermediate carrier body, the flange of the second intermediate carrier body, and the aft mount post to couple the first blade track segment to the first intermediate carrier body and the second intermediate carrier body, 
 repeating the previous steps until the assembled plurality of blade track segments and plurality of intermediate carrier bodies form a full hoop turbine shroud, and 
 arranging the full hoop turbine shroud in a gas turbine engine. 
 
     
     
       18. The method of  claim 17 , wherein each of the plurality of intermediate carrier body is shaped to form at least two intermediate carrier retainers that each extend radially from the intermediate carrier body, and wherein the step of arranging the full hoop turbine shroud in the gas turbine engine includes aligning the at least two intermediate carrier retainers of each intermediate carrier body of the plurality of intermediate carrier bodies with corresponding holes and coupling the at least two intermediate carrier retainers of each intermediate carrier body of the plurality of intermediate carrier bodies with a carrier included in the gas turbine engine. 
     
     
       19. The method  claim 18 , wherein edges of the flange included in each intermediate carrier body of the plurality of intermediate carrier bodies are spaced apart axially from edges of a circumferential end of the intermediate carrier body. 
     
     
       20. The method of  claim 18 , wherein the first intermediate carrier body is shaped to include a flange that extends circumferentially from the adjacent circumferential end of the first intermediate carrier body to form the groove, the flange of the first intermediate carrier body extends into a groove formed by the flange of the second intermediate carrier body to engage the flange of the second intermediate carrier body, and the one pin of the at least two first intermediate carrier pins extends axially through the flange of the first intermediate carrier body and the flange of the second intermediate carrier body to form the joint.